National Advisory Committee for Aeronautics (NACA) - 34 Matching Results

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Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction

Description: "Maintenance of a laminar boundary layer by suction was suggested recently to decrease the friction drag of an immersed body, in particular an airfoil section. The present treatise makes a theoretical contribution to this question in which, for several cases of suction and blowing, the stability of the laminar velocity profile is investigated. Estimates of the minimum suction quantities for maintaining the laminar boundary layer and estimates of drag reduction are thereby obtained" (p. 1).
Date: June 1947
Creator: Ulrich, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Lead-Bronze Bearings in the DVL Bearing-Testing Machine

Description: "The lead-bronze bearings tested in the DVL machine have proven themselves very sensitive to load changes as in comparison with bearings of light metal. In order to prevent surface injuries and consequently running interruptions, the increase of the load has to be made in small steps with sufficient run-in time between steps. The absence of lead in the running surface, impurities in the alloy (especially iron) and surface irregularities (pores) decreases the load-carrying capacity of the bearin… more
Date: June 1940
Creator: Fischer, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds (The Efficiency of Shock Diffusers)

Description: "The problem of the intake of air is treated for a missile flying at supersonic speeds and of changing the kinetic energy of the air into pressure with the least possible losses. Calculations are carried out concerning the results which can be attained. After a discussion of several preliminary experiments, the practical solution of the problem at hand is indicated by model experiments. The results proved very satisfactory in view of the results which had been attained previously and the values… more
Date: June 1947
Creator: Oswatitsch, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air Transport by Gliders: Some Technical Observations

Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
Date: June 1941
Creator: Stepniewski, Wieslaw
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General Airfoil Theory

Description: "On the assumption of infinitely small disturbances the author develops a generalized integral equation of airfoil theory which is applicable to any motion and compressible fluid. Successive specializations yield various simpler integral equations, such as Possio's, Birnbaum's, and Prandtl's integral equations, as well as new ones for the wing of infinite span with periodic downwash distribution and for the oscillating wing with high aspect ratio. Lastly, several solutions and methods for solvi… more
Date: June 1941
Creator: Küssner, H. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Italian High-Speed Airplane Engines

Description: This paper presents an account of Italian high-speed engine designs. The tests were performed on the Fiat AS6 engine, and all components of that engine are discussed from cylinders to superchargers as well as the test set-up. The results of the bench tests are given along with the performance of the engines in various races.
Date: June 1940
Creator: Bona, C. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory of Heat Transfer and Hydraulic Resistance of Oil Radiators

Description: "In the present report the coefficients of heat transfer and hydraulic resistance are theoretically obtained for the case of laminar flow of a heated viscous liquid in a narrow rectangular channel. The results obtained are applied to the computation of oil radiators, which to a first approximation may be considered as made up of a system of such channels. In conclusion, a comparison is given of the theoretical with the experimental results obtained from tests on airplane oil radiators" (p. 1).
Date: June 1942
Creator: Mariamov, N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Strength Tests on Hulls and Floats

Description: "The present report deals with strength tests on hulls and floats intended in part for the collection of construction data for the design of these components and in part for the stress analysis of the finished hulls and floats" (p. 1).
Date: June 1942
Creator: Matthaes, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

On the Symmetrical Potential Flow of Compressible Fluid Past a Circular Cylinder in the Tunnel in the Subcritical Zone

Description: "The two-dimensional symmetrical potential flow of compressible fluid past a circular cylinder placed in the center line of a straight tunnel is analyzed in second approximation according to the Jansen-Rayleigh method. The departure of the profile from the exact circular shape can be kept to the same magnitude as for the incompressible flow. The velocities in the narrowest section of the tunnel wall and at the profile edge are discussed in detail" (p. 1).
Date: June 1942
Creator: Lamla, Ernst
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Stability of Laminar Flow Past a Sphere

Description: "As a contribution to the problem of turbulence on a surface of rotation, the method of small oscillation is applied to the flow past a sphere. It was found that the method developed for two-dimensional flow is applicable without modifications. The frictional layer in the vicinity of the stagnation point of a surface of rotation is less stable against small two-dimensional disturbances than in the stagnation point itself, as proved from an analysis of the velocity distribution made by Homann" (… more
Date: June 1942
Creator: Pretsch, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Propeller Blade Stresses Caused by Periodic Displacement of the Propeller Shaft

Description: The present report deals with different vibration stresses of the propeller and their removal by an elastic coupling of propeller and engine. A method is described for protecting the propeller from unstable oscillations and herewith from the thus excited alternating gyroscopic moments. The respective vibration equations are set down and the amount of elasticity required is deduced.
Date: June 1942
Creator: Meyer, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Statistical analysis of service stresses in aircraft wings

Description: On the wing structures of modern high speed aircraft, in particular, the comparatively high-service stresses and the consistently increasing number of hours of operation during the life of the separate airplane parts make the studies of strength requirement under recurrent stresses appear of major concern. The DVL has therefore made exhaustive studies for this structural group of airplanes, some results of which are reported here.
Date: June 1942
Creator: Kaul, Hans W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Three-Component Force and Mass-Flow Measurement on a Jet Nacelle

Description: The present report contains three-component forces and mass-flow measurements on a jet nacelle at small inlet-velocity ratios v(sub A)/v(sub o) < 1. The mass-flow measurement on two cross sections of the nacelle demonstrate the local-velocity distribution with varying flow and angle of attack.
Date: June 1947
Creator: Ilgmann, G. & Möller, E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Photographic Profile Recorder for Airscrews and Wing Models

Description: "This report describes an apparatus enabling measurements of bodies to be made photographically, where other methods would be difficult. It is especially useful in the case of airscrews and wing models. The utility of the machine is shown by a few examples of profile records" (p. 1).
Date: June 1946
Creator: Kuhl, R. & Raab, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Description of Russian Aircraft Engines "AM 35" and "AM 38"

Description: The Russian AM 35 and AM 38 aircraft engines have superchargers with a swirl throttle, which appears to be a purely Russian development. This paper gives the results of test runs of the two engines, including the effects of the swirl throttle on engine performance.
Date: June 1947
Creator: Denkmeier, H. & Gross, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift Increase by Blowing Out Air, Tests on Airfoil of 12 Percent Thickness, Using Various Types of Flap

Description: "The NACA 23012-4 airfoil was investigated for the purpose of increasing lift by means of blowing out air from the wing, in conjunction with the effect of plain flap of variable contour and slotted flap of 25 percent chord length. The wing also was provided with a hinged nose, to be deflected at will. Air was blown out from the wing immediately in front of the flap; also at the opening between wing and hinged nose,tangentially to the surface of the wing" (p. 1).
Date: June 1947
Creator: Schwier, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Test Report on Three-and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Elliptic Wing)

Description: "The report UM No. 1023/1 which presented the results of measurements for a series of trapezoidal wings was the beginning of a series on wings with aspect ratio 1 to 3 and various contours. In report No. 1023/1 the aspect ratio (Lambda = 4/3) remained the same; the tapering was modified. The present report gives the results of the series of elliptic wings. Here the aspect ratio varies from 1 to 2 with the sweepback. The contour is formed by elliptic arcs. The influence of sweepback and contour … more
Date: June 1947
Creator: Lange & Wacke
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

General Characteristics of the Flow through Nozzles at Near Critical Speeds

Description: The characteristics of the position and form of the transition surface through the critical velocity are computed for flow through flat and round nozzles from subsonic to supersonic velocity. Corresponding considerations were carried out for the flow about profiles in the vicinity of sonic velocity.
Date: June 1947
Creator: Sauer, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compression Shocks of Detached Flow

Description: "It is known that compression shocks which lead from supersonic to subsonic velocity cause the flow to separate on impact on a rigid wall. Such shocks appear at bodies with circular symmetry or wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high a back pressure. The form of the compression shocks observed therein is investigated" (p. 1).
Date: June 1947
Creator: Eggink
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Six-Component Measurements on a Straight and a 35 Degree Swept-Back Trapezoidal Wing With and Without Split Flaps

Description: In accord with me test program (published in reference 7) the wing in question is briefly designated as No. 5. It differs from the rectangular wing discussed in reference 7 by its taper and from the 35 degree swept-back trapezoidal wing treated in reference 8 by the absence of sweepback.
Date: June 1947
Creator: Thiel, G. & Weissinger, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Computation of Thin-Walled Prismatic Shells

Description: "We consider a prismatic shell consisting of a finite number of narrow rectangular plates and having in the cross-section a finite number of closed contours (fig. 1(a)). We shall assume that the rectangular plates composing the shell are rigidly joined so that there is no motion of any kind of one plate relative to the others meeting at a given connecting line. The position of a point on the middle prismatic surface is considered to be defined by the coordinate z, the distance to a certain init… more
Date: June 1949
Creator: Vlasov, V. Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Contribution to the Problem of Flow at High Speed

Description: Report divided into two sections about flow problems encountered at high speeds. The topics include: 1) A Few General Remarks Covering the Prandtl-Busemann Method; and 2) Effect of Compressibility in Axially Symmetrical Flow around an Ellipsoid.
Date: June 1949
Creator: Schmieden, C. & Kawalki, K. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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